Torpedo suspension band



June 11, 1968 G. CHAKOIAN ET AL 3,387,537

TORPEDO SUSPENSION BAND 2 Sheets-Sheet l Fild Feb. 17, 1967 INVENTORS.GEORGE CHAKOIAN RUSSELL T. CROWELL NATHAN M. SOUTHWICK BY V. C. MULLERROY MILLER ATTORNEYS.

June 11, 1968 CHAKOIAN ET AL 3,387,537

TORPEDO SUSPENSION BAND Filed Feb. 17, 1967 2 Sheets-Sheet 2 INVENTORS.

GEORGE CHAKOIAN RUSSELL T. CROWELL NATHAN M. SOUTHWICK BY V. C. MULLERROY MILLER ATTORNEYS.

United States Patent Office Patented June 11, 1968 Ma..- a.

ABSTRACT OF THE DISCLOSURE A latching mechanism including a sensitivetrigger, maintains band locked on a missile and releases it from themissile upon application of a relatively small force applied to atrigger actuating wedge, which is separated from the band by a parachuteor a static line.

This invention relates to breakaway bands for suspending and launchingmissiles, such as torpedoes, from aircraft and more particularly toimprovements in bands of the type disclosed in the Patents to Rhodes3,077,818, Barrowman 2,826,119 and Niedling 2,786,392.

Of the patents just referred to, the patent to Barrowman is the mostclosely related to this invention in that a pivoted suspension lug (21)looks one end of the band against separation, the lug being restrainedagainst pivotal movement by a releasable locking plate or key (22) whichis removed by a lanyard (37) attached to the aircraft, thus effectingrelease at some distance below the aircraft and preventing the separatedband from striking rearward portions of the aircraft. Among thedisadvantages of the Barrowman band are the requirement that the pull onthe lanyard must be substantially vertical to remove the locking plateor key from its retaining slots and the tension in the lanyard must besuflicient to overcome the high locking force exerted between thepivoted lug and the locking plate.

One of the objects of the present invention is to provide a suspensionband which may be released from a missile by a lanyard, the pull ofwhich may be in various directions relative to the direction of fall ofthe missile.

Another object is to provide a release mechanism which, with a relativesmall tension in the lanyard, may trigger the release againstconsiderably higher locking forces.

Another object is to provide a suspension band of simplifiedconstruction with a minimum number of parts.

Still further objects, advantages, and salient features will become moreapparent from the description to follow, the appended claims, and theaccompanying drawing, in which:

FIG. 1 is a perspective of the invention;

FIG. 2 is a section and side elevation taken on line 2-2, FIG 3;

FIG. 3 is a top plan as viewed in the direction of arrow 3, FIG. 2; and

FIG. 4 is a view, like FIG. 2, showing the parts in released position.

Referring first to FIG. 1, the invention comprises a suspension devicewhich encircles a missile (not shown) which is suspended by a moveablehook of a bomb rack (not shown) which engages lug 12, this being one ofa pair of identical devices disposed at spaced points along the lengthof the missile, as is conventional in the prior art referred to.

Referring to FIGS. 2 and 3, device 10 comprises a platelike saddlemember 14 to which is secured a pair of bands 16 having looped ends 18which engage ends of a cross pin 20 which is secured to a lug 22 on thesaddle member by a bolt 24 which passes through the center of the pinand threadedly engages the lug. The other ends of the bands have likelooped ends 26 which engage ends of a cross pin 28.

A pair of parallel upstanding flanges 30 are integrally formed on thesaddle member, providing a slot 32 between the flanges. The lower end oflug 12 is disposed within the slot and pivotally connected to theflanges by a pin 34. As best shown in FIG. 2, each flange is providedwith an inclined ramp 36, the two ramps and a curved portion 38 on thelug forming a V block which is engaged by pin 28. When the lug isrestrained against pivotal movement in a clockwise direction, as viewedin FIG. 2, it will be apparent that the tension in the bands forces pin28 into the V block in the direction of arrow 40, preventing release ofthe bands from the missile which they encircle. Referring now to FIG. 4,the parts are shown in a position in which lug 12 has been permitted torotate in a clockwise direction. As will be apparent, the V block hasnow opened, permitting pin 28 to slide over one side of the lug, thusreleasing ends of the bands from the saddle member assembly.

The lug locking means comprises a blocking member 42, a trigger 44 and awedge 46 for actuating the trigger. Member 42 is disposed within slot32, one end being pivoted to flanges 30 by a pin 48, its other endengaging one side of lug 12 as best shown in FIG. 2. Trigger 44 isprovided with a pair of oppositely extending abutment pins 50 each ofwhich engage an inclined ramp 52 on a flange 30. Its left end, as shownin FIGS. 3 and 4, is provided with a half round notch 54 which engages across pin 56 carried by member 42. Wedge 46 is provided withintersecting surfaces 58 (FIG. 4), which abut like intersecting surfaces60, 61 at the left end of the flanges, and wedging edges 62 formed as aV. Trigger 44 and blocking member 42 form links of a toggle mechanismwhich, due to the choice of the angle on ramps 52, tend to force pins 50down the ramp to an overcenter self locking position by the tension inbands 16. If desired, a safety wire (not shown) may be secured to theparts to prevent premature lifting of tail 64 of trigger 44.

In operation, a band unit is wrapped around the missile and pin isdisposed in the position shown in FIG. 2 with the lug also in suchposition. The lug blocking memher is then swung to the position shown,the wedge lain into the position shown, and the trigger 44 inserted sothat its notch 54 engages pin 56 and its pins engage ramps 52. The bandis then tensioned as desired by bolt 24.

Shortly after launching a missile, when it is clear of its carryingaircraft, wedge 46 is removed from beneath the tail of the trigger. Thismay be eifected by a static line or lanyard having one end fixed to theaircraft and its other end secured to one end of the wedge. In anothermode of removing the wedge, one end of the lanyard is aflixed to aparachute which deploys after dropping the missile, opening of theparachute providing a tension on a lanyard to remove the wedge. In thefirst mentioned mode, the wedge serves as a lever, pivoting about oneend and raising tail 64. In the second mode, the wedge is pulled in thedirection of its longitudinal axis and one of surfaces 62 engages tail64, also lifting it. As the tail lifts, pins 50 slide upwardly alongramps 52 until they move out of engagement with the ramps. At thispoint, the tension in the bands moves the parts to unlocked position andtrigger 44 flys free from engagement with the blocking member which isforced by the lug to the position shown in FIG. 4. Since the V block isnow opened, pin 28 is free to pass over the lug and release the entireband assembly from the missile.

FIG. 4 illustrates a refinement to the wedge wherein it is provided witha pair of intersecting camming surfaces 66. Surfaces 61 on the ends ofthe flanges are milled to the same angle. As the wedge is movedtrans-verse to the flanges, one of surfaces 66 engages a surface 61 andcams 3 one end of the wedge outwardly as it is being removed frombeneath the tail.

Obviously many modifications and variations of the present invention arepossible in the light of the above teachings. It is therefore to beunderstood that within the scope of the appended claims the inventionmay be practiced otherwise than as specifically described.

What is claimed is:

1. A break-away suspension device for an aircraft launched elongatedmissile, such as a torpedo, comprising;

(1) a saddle member adapted to be disposed at the top of the missilehaving a pair of spaced upwardly extending flanges extending transverseto the missile axis, forming an upwardly open channel therebetween,

(2) a suspension lug having a lower portion disposed between the flangesand pivoted thereto for movement in a plane perpendicular to the missileaxis, said lug having an aperture therein for removably receiving a bombrack hook,

(3) axially aligned inclined surfaces on said flanges forming one faceof a V block,

(4) a surface at one side of said lug forming the other face of the Vblock,

(5) a longitudinally extending circular pin abutting the faces of the Vblock having a pair of spaced tensioned bands afiixed thereto, one toeach end thereof, and encircling the missile, their other ends beingsecured to the saddle member, and

(6) means for preventing pivotal movement of said lug to therebymaintain a predetermined angle between said faces of the V block whichprevents movement of the pin over the top of the lug, said meanscornprising;

(a) a blocking member having one end disposed between the flanges andpivoted thereto, its other 4 end engaging said lug at the side oppositethe V block,

(b) a trigger disposed above said blocking member having one endpivotally engaging said other end of the blocking member and havingintermediate portions slideably engaging inclined ramps on said flanges,the construction being such that said blocking member and trigger form atoggle mechanism adapted to tighten toward a locked position uponapplication of increasing force applied between the lug and blockingmember, the other end of said trigger forming a tail adapted to belifted, for moving said intermediate portions off of the inclined ramps,and

(c) a removable Wedge disposed beneath said tail adapted to wedginglyengage the tail and portions of the saddle member for lifting the tailand moving said intermediate portions ofi of the inclined ramp tothereby permit the blocking member to rotate, and the lug to rotate, topermit said pin to move over the top of the lug to thereby release thedevice from the missile as a unit.

2. Apparatus in accordance with claim 1 wherein said Wedge membercomprises a pair of wedging edges, forming a V, their intersection beingdisposed beneath the tail, the construction being such that longitudinalmovement of the wedge member in either direction causes one or the otherof the edges to engage the tail and lift same.

References Cited UNITED STATES PATENTS 2,786,392 3/ 1957 Niedling 89-152,826,119 3/ 1958 Barrowman 89-l.5 3,077,818 2/1963 Rhodes 89-15 SAMUELW. ENGLE, Primary Examiner.

